Aircraft air inlet diverter assemblies with improved aerodynamic characteristics

Abstract

Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.

What is claimed is: 
     
       1. A diverter assembly for an aircraft air inlet opening, wherein the diverter assembly comprises:
 a diverter structure comprising a base member attached to a fuselage region of the aircraft so as to at least partially surround forward and lateral edge portions of a perimetrical edge defining the air inlet opening, an upper support member spaced above the base member, and an upright member connecting the base member to the support member, and 
 a fairing mounted to a forward portion of the support member of the diverter structure so that the fairing is mounted above the aircraft fuselage region forwardly of the air inlet opening, wherein 
 the fairing comprises an apex end forwardly of the air inlet opening and laterally divergent side regions, and wherein 
 the fairing includes a rear edge region disposed over a forward edge of the air inlet opening. 
 
     
     
       2. The diverter assembly as in  claim 1 , wherein the fairing is a solid structure which defines a relatively smooth ramp which slopes aftward toward a forward edge of the in the air inlet opening to thereby avoid airflow detachment forwardly of the air inlet opening. 
     
     
       3. The diverter assembly as in  claim 1 , wherein the air inlet opening includes an air scoop extending outwardly therefrom. 
     
     
       4. The diverter assembly as in  claim 1 , wherein the diverter structure has a substantially S-shaped cross-section comprised of the base member, the upper support member and the upright member. 
     
     
       5. The diverter assembly as in  claim 1 , further comprising a fairing support bracket positioned along a forward edge of the air inlet opening rearwardly of the diverter structure, wherein an aft edge of the fairing is attached to the fairing bracket. 
     
     
       6. The diverter assembly as in  claim 1 , wherein the fairing comprises a concavely curved aft region defining a corresponding concavely curved aft edge, wherein the laterally divergent side regions join the forward apex and aft regions of the fairing. 
     
     
       7. The diverter assembly as in  claim 6 , further comprising an S-shaped fairing bracket positioned along a forward edge of the air inlet opening rearwardly of the diverter structure, wherein an aft edge of the fairing is attached to the fairing bracket. 
     
     
       8. The diverter assembly as in  claim 7 , wherein the fairing bracket includes a lower base flange, an upper support flange and an intermediate support member which rigidly joins the lower base and upper support flanges to one. 
     
     
       9. The diverter assembly as in  claim 8 , wherein the upper support flange is positioned relative to the lower base flange so that an aft edge of the fairing overhangs a forward edge of the air inlet opening. 
     
     
       10. The diverter assembly as in  claim 3 , wherein the diverter is a generally U-shaped member comprising the base member, the support member and the upright member. 
     
     
       11. The diverter assembly as in  claim 1 , wherein the fairing includes an aft region which slopes downwardly and rearwardly towards the air inlet opening. 
     
     
       12. An aircraft which comprises a diverter assembly as in any one of  claims 1 - 11 .